The Efficiency of Different Flow Control Methods on a Vertical Tail

Scholz, Peter; Singh, Vickram M.; Gebhardt, Anna; Löffler, Stephan; Weiss, Julien

doi:10.2514/6.2020-1537

Cited by 5 publications

(4 citation statements)

References 20 publications

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“…It is possible to reduce the lip height uncertainty using alternative actuator design. Examples include multiple plena (Oswald et al 2019;Scholz et al 2020) instead of a single one, and more adjustment bolts through the lid, rendering the lid less susceptible to bending. Such designs can reduce the slot height uncertainty to an estimated b h S ≈ 5% .…”

Section: Setup Systematic Uncertaintymentioning

confidence: 99%

The uncertainty of the experimentally-measured momentum coefficient

Semaan

2020

Exp Fluids

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We quantify the uncertainty of the momentum coefficient, $$C_{\mu}$$ C μ , for six different experimental approaches. The approaches vary depending on compressibility effects and on the utilized acquisition equipment to measure the product of the mass flow rate with the jet exit velocity. The uncertainty of the directly-measured variables is propagated into the momentum coefficient using the Taylor expansion method to the first order. All relevant random and systematic uncertainties are meticulously quantified and listed. The analysis reveals unacceptably high uncertainty of the momentum coefficient under certain settings. Practical solutions to minimize the sources of uncertainty are then proposed and analyzed. The proposed improvements on the benchmark example of a Coanda actuator with a high aspect ratio slot reduce the uncertainty of $$C_{\mu}$$ C μ significantly but not sufficiently, as it remains at a non-negligible value of $$\approx 11\%$$ ≈ 11 % for the best scenario. Finally, a list of practical recommendations and guidelines on how to accurately estimate the momentum coefficient experimentally is provided. Graphic abstract

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Section: Setup Systematic Uncertaintymentioning

confidence: 99%

The uncertainty of the experimentally-measured momentum coefficient

Semaan

2020

Exp Fluids

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“…The experimental results show that the impact of an unsteady jet on restraining flow separation is better than that of a steady jet. The scholars Loeffler and Scholz et al, (2020) [20][21][22] in Germany carried out active flow control at the leading edge and stabilizer hinge increasing the vertical tail lateral force, the under different slip angles and rudder deflection angles. The experimental results show that active flow control at the front edge of the vertical tail stabilizer can significantly improve the flow separation on the stabilizer surface at large lateral slip angles, while reducing resistance.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study of Vertical Tail Model Flow Control Based on Oscillating Jet

Cao

Dong

et al. 2023

Applied Sciences

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In this paper, wind tunnel experiments are conducted to study the control law and mechanism of oscillating jet flow control to improve the aerodynamic characteristics of the vertical tail when a civil aircraft encounters left side gust or significant crosswind during takeoff and landing. We measured the vertical tail scaling model’s aerodynamics, spatial flow field, and surface pressure when the Reynolds number was 2.12 × 105. The maximum momentum coefficient of the oscillating jet actuator reaches 0.332%. In addition, we studied the flow control effect of the three-dimensional vertical tail scaled model in different spanwise positions. The experimental results show that the oscillating jet at the rear edge of the stabilizer can significantly increase the lateral force of the vertical tail, and the increment of the lateral force can reach 36.5% under the worst condition of the negative side slip angle of the vertical tail. We can improve the lateral force coefficient of the vertical tail model by applying flow control alone at different spanwise locations. The wing root’s control effect and the vertical tail’s middle section are better than the wing tip’s. The oscillating jet can effectively restrain the flow separation on the rudder. In addition, the input of a high-energy jet “ejects” the mainstream, which increases the flow velocity at the side of the vertical tail actuator. It increases the circulation of the vertical tail. The oscillating jet flow control technology can effectively improve the vertical tail’s steering efficiency and increase the vertical tail’s lateral force, which is of great significance in improving the safety and economy of civil aircraft.

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“…Scholz and Singh (2020) investigated the effect of different flow control methods on a vertical tail. They studied each method in detail and evaluated the ability of different methods to increase the lateral force of the aircraft tail (Scholz and Singh, 2020). Khalil et al (2020) used active flow control methods to reduce aircraft wing load.…”

Section: Introductionmentioning

confidence: 99%

“…Their numerical simulation shows that the use of flow jets to control the flow is very efficient and causes the flow to remain attached to the surface (Kewei et al , 2020). Scholz and Singh (2020) investigated the effect of different flow control methods on a vertical tail. They studied each method in detail and evaluated the ability of different methods to increase the lateral force of the aircraft tail (Scholz and Singh, 2020).…”

Section: Introductionmentioning

confidence: 99%

Flow control method by applying flexible shells procedure in transonic flow

Saber

Djavareshkian

2021

AEAT

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Purpose In the present research, the effect of the flexible shells method in unsteady viscous flow around airfoil has been studied. In the presented algorithm, due to the interaction of the aerodynamic forces and the structural stiffness (fluid-structural interaction), a geometrical deformation as the bump is created in the area where the shock occurs. This bump causes instead of compressive waves, a series of expansion waves that produce less drag and also improve the aerodynamic performance to be formed. The purpose of this paper is to reduce wave drag throughout the flight range. By using this method, we can be more effective than recent methods throughout the flight because if there is a shock, a bump will form in that area, and if the shock does not occur, the shape of the airfoil will not change. Design/methodology/approach In this simulation pressure-based procedure to solve the Navier-Stokes equation with collocated finite volume formulation has been developed. For this purpose, a high-resolution scheme for fluid and structure simulation in transonic flows with an arbitrary Lagrangian-Eulerian method is considered. To simulate Navier-Stokes equations large eddy simulation model for compressible flow is used. Findings A new concept has been defined to reduce the transonic flow drag. To reduce drag force and increase the performance of airfoil in transonic flow, the shell can be considered flexible in the area of shock on the airfoil surface. This method refers to the use of smart materials in the aircraft wing shell. Originality/value The value of the paper is to develop a new approach to improve the aerodynamic performance and reduce drag force and the efficiency of the method throughout the flight. It is noticeable that the new algorithm can detect the shock region automatically; this point was disregarded in the previous studies. It is hoped that this research will open a door to significantly enhance transonic airfoil performance.

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The Efficiency of Different Flow Control Methods on a Vertical Tail

Cited by 5 publications

References 20 publications

The uncertainty of the experimentally-measured momentum coefficient

The uncertainty of the experimentally-measured momentum coefficient

Experimental Study of Vertical Tail Model Flow Control Based on Oscillating Jet

Flow control method by applying flexible shells procedure in transonic flow

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